CN107380482A - Pneumatic accessories of aircraft universal test platform - Google Patents
Pneumatic accessories of aircraft universal test platform Download PDFInfo
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- CN107380482A CN107380482A CN201710647788.9A CN201710647788A CN107380482A CN 107380482 A CN107380482 A CN 107380482A CN 201710647788 A CN201710647788 A CN 201710647788A CN 107380482 A CN107380482 A CN 107380482A
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- 238000012360 testing method Methods 0.000 title claims abstract description 203
- 239000000295 fuel oil Substances 0.000 claims abstract description 16
- 238000009423 ventilation Methods 0.000 claims abstract description 14
- 239000003638 chemical reducing agent Substances 0.000 claims description 23
- 230000006837 decompression Effects 0.000 claims description 13
- 238000010943 off-gassing Methods 0.000 claims description 12
- 206010008469 Chest discomfort Diseases 0.000 claims description 4
- 230000007613 environmental effect Effects 0.000 abstract description 8
- 239000010729 system oil Substances 0.000 abstract description 8
- 238000001514 detection method Methods 0.000 abstract description 6
- 238000009434 installation Methods 0.000 abstract description 5
- 238000007789 sealing Methods 0.000 description 11
- 238000013461 design Methods 0.000 description 10
- 238000007689 inspection Methods 0.000 description 8
- 238000002474 experimental method Methods 0.000 description 6
- 230000007935 neutral effect Effects 0.000 description 6
- 238000011056 performance test Methods 0.000 description 6
- 230000033228 biological regulation Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000003321 amplification Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 210000002445 nipple Anatomy 0.000 description 2
- 238000003199 nucleic acid amplification method Methods 0.000 description 2
- 239000000344 soap Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 235000008331 Pinus X rigitaeda Nutrition 0.000 description 1
- 235000011613 Pinus brutia Nutrition 0.000 description 1
- 241000018646 Pinus brutia Species 0.000 description 1
- 238000005273 aeration Methods 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000032258 transport Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention relates to a kind of pneumatic accessories of aircraft universal test platform, including testing stage body, the outside of the test stage body is provided with console and control panel, cold gas system and electrical system is provided with the testboard body, the electrical system is connected with the cold gas system, is powered for the cold gas system；The cold gas system includes being used to test the first test cell of plain edition pneumatic accessories, the second test cell for testing special type pneumatic accessories and the flow test units for testing aircraft fuel oil ventilation pressure charging system pneumatic accessories.Can be ventilated to aircraft cold gas system, the environmental control system and fuel oil pneumatic accessories of pressure charging system of the present invention carries out the performance detection of pressure and flow, meet before the pneumatic accessories installation of cold gas system on aircraft, environmental control system and fuel oil ventilation pressure charging system and basic demand during regular working to its performance detection.
Description
Technical field
The invention belongs to aircraft accessory technical field of measurement and test, is related to pneumatic accessories of aircraft measuring technology, specifically, is related to
A kind of pneumatic accessories of aircraft universal test platform, the gas of cold gas system, environmental control system and fuel oil ventilation pressure charging system on aircraft
To the performance detection of pneumatic accessories before dynamic annex installation and during regular working.
Background technology
Because pneumatic system has the characteristics that safe to use, reliable, long lifespan, pneumatics is used on aircraft, pneumatically
Technology is mainly used in aircraft cold gas system, environmental control system and fuel oil ventilation pressure charging system.It is related in said system pneumatic attached
Before part installation or pneumatic accessories regular working is rear, it is necessary to test the performance of pneumatic accessories, to avoid because of gas for a period of time
Dynamic annex damage or cisco unity malfunction cause Flight Safety problem, so that it is guaranteed that the rate of good of aircraft.
At present, the performance test bed function of most of pneumatic accessories is relatively single, and aircraft utilization unit is by objective
The restriction of condition, many test equipments for being also not equipped with matching with pneumatic accessories using unit.Therefore, develop a kind of pneumatic
Annex universal test platform, it disclosure satisfy that the pneumatic accessories installation of aircraft cold gas system, environmental control system and fuel oil ventilation pressure charging system
Performance detection after preceding and regular working, it is of great significance to ensureing aircraft rate of good, improving aircraft safety tool.
The content of the invention
The present invention is in view of the above-mentioned problems existing in the prior art, there is provided a kind of pneumatic accessories of aircraft universal test platform, energy
Enough pneumatic accessories that pressure charging system is ventilated to aircraft cold gas system, environmental control system and fuel oil carry out pressure and the performance of flow is examined
Survey.
In order to achieve the above object, the invention provides a kind of pneumatic accessories of aircraft universal test platform, including stage body is tested,
The outside of the test stage body is provided with console and control panel, and cold gas system and electrical system are provided with the testboard body,
The electrical system is connected with the cold gas system, is powered for the cold gas system；
The cold gas system includes being used to test the first test cell of plain edition pneumatic accessories, for testing special type gas
Second test cell of dynamic annex and the flow test units for testing aircraft fuel oil ventilation pressure charging system pneumatic accessories；
First test cell includes the first pipeline that one end is provided with air inlet ozzle, the other end is provided with outlet ozzle, institute
State on the first pipeline along outgassing direction be sequentially provided with range be 0-25MPa pressure gauge, it is 5MPa pressure reducers, brake modulator, cold
Air cock and the pressure gauge that range is 0-1.6MPa；Three branch lines, the connection of the first branch line are connected with first pipeline
On the first pipeline between the air inlet ozzle and the 5MPa pressure reducers, second branched pipe road and Three branched pipe Lu Junlian
It is connected on the first pipeline between the 5MPa pressure reducers and the brake modulator；The outlet side of each branch line is equipped with
Outlet ozzle, air cock is sequentially provided with along outgassing direction on first branch line and second branched pipe road and range is
0-16MPa pressure gauge, it is 0-10MPa's to be sequentially provided with air cock and range along outgassing direction on the second branched pipe road
Pressure gauge, it is 0- to be sequentially provided with 0.3MPa pressure reducers, air cock and range along outgassing direction on the Three branched pipe road
0.4MPa pressure gauge；
Second test cell is included for the first test loop for testing electromagnetism cold air valve, decompression of being braked for test
Second test loop of valve, the 3rd test loop for testing pressure-releasing electromagnetic valve, for testing first brake pressure regulator and brake
4th test loop of car differentiator, the 5th test loop for testing the second brake pressure regulator and brake distributor, it is used for
6th test loop of test brake amplifier, the 7th test loop for tested cylinder and jettron and for increasing
The boost-up circuit of tested pneumatic accessories bleed pressure；
The flow test units include being used for test scope in 16m l/mi n-10m3The low discharge of gas flow in/h
Test loop and for test scope in 10-100m3The big flow test loop of gas flow in/h.
Preferably, the outlet nipple end on first pipeline and each branch line is equipped with relief valve.
Preferably, the air inlet ozzle and the range the first pipeline between 0-25MPa pressure gauge are sequentially provided with cold
Air filter and check valve.
Preferably, first test loop includes being connected with the first pipeline the second pipeline, it is connected with the 3rd branch path
The 3rd pipeline and electromagnetism air cock air inlet ozzle is connected with the electromagnetism cold air valve, second pipeline and the 3rd pipeline
It is connected with electromagnetism air cock air inlet ozzle；Second pipeline connects gas cylinder, is sequentially provided with second pipeline
Air inlet switch and the pressure gauge that range is 0-16MPa；3rd pipeline connects low pressure gas cylinder, is set successively on the 3rd pipeline
There is air inlet switch to be provided with the pressure gauge that range is 0-10MPa.
Preferably, second test loop includes the 4th pipeline that is connected with first pipeline and with the described 4
Pipeline connects 1.5L high pressure cold bottles, and it is 0- to be sequentially provided with air inlet switch, Aircraft Brake Decompression Valve and range on the 4th pipeline
16MPa pressure gauge.
Further, the 3rd test loop includes the 5th pipeline and the described 5th being connected with first pipeline
4th branch line of pipeline connection, the 0.5L low pressure gas cylinders that are connected with the 5th pipeline and it is connected with the 4th branch line
1L low pressure gas cylinders；5MPa pressure reducers are sequentially provided with 5th pipeline, the range for measuring admission pressure is 0-10MPa
Pressure gauge, air inlet switch, pressure-releasing electromagnetic valve and for measure outlet pressure range be 0-10MPa pressure gauge；It is described
4th branch line is connected on the 5th pipeline between air inlet switch and the pressure-releasing electromagnetic valve.
Further, the 4th test loop include be connected with the Three branched pipe road the 6th pipeline, with it is described
6th pipeline connection quintafurcation pipeline, the 1.5L high pressure colds bottle being connected with the 6th pipeline and with the quintafurcation
The 0.75L low pressure air bottles of pipeline connection, are sequentially provided with air inlet switch, first brake pressure regulator on the 6th pipeline and are used for
The range for measuring outlet pressure is 0-10MPa pressure gauge；The quintafurcation pipeline is connected to the first brake pressure regulator
On 6th pipeline of gas outlet, it is 0- that air inlet switch, brake differentiator and range are sequentially provided with the quintafurcation pipeline
10MPa pressure gauge.
5th test loop includes the 7th pipeline being connected with the Three branched pipe road and the 7th pipeline connects
Connect the 6th branch line, 2L gas cylinders being connected with the 7th pipeline and low with the 6th branch line 1L being connected
Air bottle is pressed, air inlet switch, the second brake pressure regulator and the amount for measuring outlet pressure are sequentially provided with the 7th pipeline
Journey is 0-10MPa pressure gauge；6th branch line is connected to the 7th pipeline of the second brake pressure regulator gas outlet
On, the pressure gauge that air inlet switch, brake distributor and range are 0-10MPa is sequentially provided with the 6th branch line.
Preferably, the 6th test loop includes the 8th pipeline of the 3rd branch path connection and managed with the described 8th
The 0.5L low pressure gas cylinders of road connection, air inlet switch, brake amplifier are sequentially provided with the 8th pipeline and for measuring outlet
The range of pressure is 0-10MPa pressure gauge；The gas outlet of the brake amplifier and the described second brake pressure regulator passes through the
Seven branch lines connect, and the 7th branch line is provided with air inlet switch.
7th test loop include the 9th pipeline that is connected with the Three branched pipe road and with the 9th pipeline
The jettron of connection and the cylinder being connected with the jettron, the 9th pipeline are provided with air inlet switch, the gas
The jettron of dynamic switch is received top fitting and is connected with the cylinder receipts top fitting of the cylinder, and the jettron of the jettron is put
Lower ozzle puts down ozzle with the cylinder of the cylinder and is connected.
Preferably, the boost-up circuit includes the tenth pipeline being connected with first pipeline, and the tenth pipeline goes out
Gas end is provided with outlet ozzle, on the tenth pipeline using this be provided with 5MPa pressure reducers, air inlet switch, range as 0-10MPa pressure
Power table, jettron, booster, for measure booster outlet pressure range be 0-25MPa pressure gauge, go out air cock,
The pressure gauge that range for measuring output pressure is 0-25MPa；The jettron of the jettron puts down ozzle and passes through pipe
Road is connected with the low pressure chamber of the booster, and the jettron of the jettron receives top fitting and passes through the pipeline provided with check valve
It is connected with the high pressure chest of the booster.
Preferably, the low discharge test loop includes the pressure that inlet end is provided with air inlet ozzle and range is 0-1.6MPa
The air inlet pipeline of table, the air inlet pipeline are connected with multiple flowmeters for testing different flow, the range of each flowmeter
Differ, the range is to be equipped with test on the air inlet pipeline between 0-1.6MPa pressure gauge and each flowmeter to open
Close；The big flow test loop includes the air inlet pipe for the pressure gauge that inlet end is provided with air inlet ozzle and range is 0-1.6MPa
Road, it is 10-100m that the air inlet pipeline, which is connected with range,3/ h flowmeter, the flowmeter and the range are 0-1.6MPa
Pressure gauge between be provided with test switch.
Compared with prior art, the advantages and positive effects of the present invention are：
The present invention can carry out pressure to the pneumatic accessories of aircraft cold gas system, environmental control system and fuel oil ventilation pressure charging system
, can also be to the sealing of special type pneumatic accessories, sensitivity, accuracy and intake and exhaust speed etc. with the performance detection of flow
Performance parameter detect, meet cold gas system on aircraft, environmental control system and fuel oil ventilation pressure charging system pneumatic accessories installation before and
To the basic demand of its performance detection during regular working.
Brief description of the drawings
Fig. 1 is the test philosophy figure of cold gas system in testboard of the embodiment of the present invention.
Fig. 2 is the test philosophy figure of the test cell of the embodiment of the present invention first.
Fig. 3 is the test philosophy figure of the test loop of the embodiment of the present invention first.
Fig. 4 is the test philosophy figure of the test loop of the embodiment of the present invention second.
Fig. 5 is the test philosophy figure of the test loop of the embodiment of the present invention the 3rd.
Fig. 6 is the test philosophy figure of the test loop of the embodiment of the present invention the 4th.
Fig. 7 is the test philosophy figure of the test loop of the embodiment of the present invention the 5th.
Fig. 8 is the test philosophy figure of the test loop of the embodiment of the present invention the 6th.
Fig. 9 is the test philosophy figure of the test loop of the embodiment of the present invention the 7th.
Figure 10 is the test philosophy figure of boost-up circuit of the embodiment of the present invention.
Figure 11 is the test philosophy figure of flow test units of the embodiment of the present invention.
1st, air inlet ozzle, 2, cold air filter, 3, check valve, 4,5MPa pressure reducers, the 5, second brake modulator, 6,0.3MPa subtracts
Depressor, 7, first brake pressure regulator, 8：Brake differentiator, 9,1.5L high pressure cold bottles, 10,0.75L low pressure air bottle, 11, stop
Car distributor, 12,2L gas cylinders, 13,1L low pressure gas cylinders, 14, brake amplifier, 15,0.5L low pressure gas cylinders, 16,16-
160mL/min flowmeter, 17,0.16-1.60L/min flowmeter, 18,0.1-1m3/ h flowmeter, 19,1-10m3/ h's
Flowmeter, 20,10-100m3/ h flowmeter, 21,0-25MPa pressure gauge, 22,0-16MPa pressure gauge, 23,0-10MPa
Pressure gauge, 24,0-1.6MPa pressure gauge, 25,0-0.16MPa pressure gauge, 26, Aircraft Brake Decompression Valve, 27, jettron,
28th, check valve, 29, booster, 30, electromagnetism cold air valve, 31, gas cylinder, 32, low pressure gas cylinder, 33, outlet ozzle, 34, outlet
Ozzle, 35, outlet ozzle, 36, outlet ozzle, 37, outlet ozzle, 38, jettron receive top fitting, 39, jettron puts down
Ozzle, 40, cylinder receive top fitting, 41, cylinder put down ozzle, 42, air inlet ozzle, 43, air inlet ozzle, 44, cylinder, 45, electromagnetism
Air cock air inlet ozzle, 46, air cock, 47, pressure-releasing electromagnetic valve, the 48, first pipeline, the 49, second pipeline, the 50, the 3rd pipe
Road, the 51, the 4th pipeline, the 52, the 5th pipeline, the 53, the 6th pipeline, the 54, the 7th pipeline, the 55, the 8th pipeline, the 56, the 9th pipeline,
57th, the tenth pipeline.
Embodiment
Below, the present invention is specifically described by exemplary embodiment.It should be appreciated, however, that do not entering one
In the case of step narration, element, structure and features in an embodiment can also be advantageously incorporated into other embodiment
In.
Present invention is disclosed a kind of pneumatic accessories of aircraft universal test platform, including test stage body, outside the test stage body
Portion is provided with console and control panel, and cold gas system and electrical system, the electrical system and institute are provided with the testboard body
Cold gas system connection is stated, is powered for the cold gas system；The cold gas system includes being used to test the of plain edition pneumatic accessories
One test cell, the second test cell for testing special type pneumatic accessories and for test aircraft fuel oil ventilation supercharging system
The flow test units of system pneumatic accessories.It is described in detail below in conjunction with the drawings and specific embodiments.
In order to complete the test of plain edition pneumatic accessories, referring to Fig. 1 and Fig. 2, first test cell is set including one end
There are air inlet ozzle 1, the other end to be provided with the first pipeline 48 of outlet ozzle 35, set successively along outgassing direction on first pipeline 48
It is 0-1.6MPa to have pressure gauge 21,5MPa pressure reducers 4, brake modulator 5, air cock 46 and range that range is 0-25MPa
Pressure gauge 22；Three branch lines are connected with first pipeline 48, the first branch line is connected to the air inlet ozzle 1 and institute
State on the first pipeline 48 between 5MPa pressure reducers 4, second branched pipe road and Three branched pipe road are all connected to the 5MPa and subtracted
On the first pipeline 48 between depressor 4 and the brake modulator 5；The outlet side of each branch line is equipped with outlet ozzle,
It is 0-16MPa to be sequentially provided with air cock 46 and range along outgassing direction on first branch line and second branched pipe road
Pressure gauge 22, be sequentially provided with air cock 46 along outgassing direction on the second branched pipe road and pressure that range is 0-10MPa
Power table 23, it is 0- to be sequentially provided with 0.3MPa pressure reducers 6, air cock 46 and range along outgassing direction on the Three branched pipe road
0.4MPa pressure gauge 25.
With continued reference to Fig. 1 and Fig. 2, the outlet nipple end on first pipeline 48 and each branch line is equipped with pressure release
Valve.After the completion of test, close each air cock, open relief valve, you can bleed off the cold air in test loop, it is ensured that annex and
The safety of personnel.
With continued reference to Fig. 1 and Fig. 2, it is preferred that the between the pressure gauge that the air inlet ozzle and the range are 0-25MPa
One pipeline 48 is provided with cold air filter 2 and check valve 3 with this.By the impurity in the filtering cold air of cold air filter 2, prevent from blocking test pipeline
And tested pneumatic accessories.The cold air for preventing from entering in pipeline by check valve 3 flows backwards.
In the cold gas system of aircraft in addition to plain edition pneumatic accessories, in addition to special type pneumatic accessories, such as：Electromagnetism
Cold air valve, Aircraft Brake Decompression Valve, pressure-releasing electromagnetic valve, brake pressure regulator, brake differentiator, brake distributor, brake amplifier, cylinder
With jettron etc..In order to complete the test of special type pneumatic accessories, with continued reference to Fig. 1, second test cell includes using
In the first test loop of test electromagnetism cold air valve 30, the second test loop for testing Aircraft Brake Decompression Valve 26, for testing
3rd test loop of pressure-releasing electromagnetic valve 47, for testing the 4th testing back for first brake pressure regulator 7 and the differentiator 8 that brakes
Road, the 5th test loop for testing the second brake pressure regulator 5 and brake distributor 11, brake amplifier 14 for test
6th test loop, the 7th test loop for tested cylinder 44 and jettron 27 and tested pneumatic attached for increasing
The boost-up circuit of part bleed pressure.
In order to complete the flow rate test of aircraft fuel oil ventilation pressure charging system pneumatic accessories, the flow test units include using
In test scope in 16ml/min-10m3In/h the low discharge test loop of gas flow and for test scope in 10-100m3/
The big flow test loop of gas flow in h.
Electromagnetism cold air valve is used to control aircraft to put umbrella, throw umbrella work gas circuit.I.e. when the circuit is on, inputted to cylinder cold
Gas；And during down circuitry, gas circuit is closed, while exclude the cold air in cylinder.In order to complete the test of electromagnetism cold air valve, as upper
The decision design of testboard is stated, referring to Fig. 1 and Fig. 3, first test loop includes the second pipe being connected with the first pipeline 48
Road 49, the 3rd pipeline 50 being connected with the 3rd branch path and it is connected electromagnetism air cock air inlet pipe with the electromagnetism cold air valve 30
Mouth 45, second pipeline 49 are connected with the 3rd pipeline 50 with electromagnetism air cock air inlet ozzle 45；Second pipeline 49
Gas cylinder 31 is connected, the pressure gauge 22 of air inlet switch and range for 0-16MPa is sequentially provided with second pipeline 49；It is described
3rd pipeline 50 connects low pressure gas cylinder 32, and it is 0-10MPa's that air inlet switch is sequentially provided with the 3rd pipeline 50 provided with range
Pressure gauge 23.
Aircraft Brake Decompression Valve is used to control the air inlet of aircraft emergency brake, deflation and the size for adjusting brake pressure.In order to complete
The test of Aircraft Brake Decompression Valve, as the decision design of above-mentioned testboard, referring to Fig. 1 and Fig. 4, second test loop include with
The 4th pipeline 51 and 1.5L high pressure colds bottle 9 is connected with the 4th pipeline 51 that first pipeline 48 connects, described the
The pressure gauge 22 that air inlet switch, Aircraft Brake Decompression Valve 26 and range are 0-16MPa is sequentially provided with four pipelines 51.
When pressure-releasing electromagnetic valve is used for airplane wheel generation tread flaking, the electric signal from inertial sensor is received, cut-out is stopped
Car gas circuit and the cold air of brake intracavitary is discharged, so as to solve wheel tread flaking, prevent tire blow-out.In order to complete deflation electromagnetism
The test of valve, as the decision design of above-mentioned testboard, referring to Fig. 1 and Fig. 5, the 3rd test loop includes and described first
The 5th pipeline 52 that pipeline 48 connects, the 4th branch line being connected with the 5th pipeline 52, connect with the 5th pipeline 52
The 0.5L low pressure gas cylinders 15 connect and the 1L low pressure gas cylinders 13 being connected with the 4th branch line；Set successively on 5th pipeline 52
There are pressure gauge 23, air inlet switch, the pressure-releasing electromagnetic valve 47 that 5MPa pressure reducers 4, the range for measuring admission pressure are 0-10MPa
And the pressure gauge 23 that the range for measuring outlet pressure is 0-10MPa；4th branch line is connected to air inlet switch
On the 5th pipeline 52 between the pressure-releasing electromagnetic valve 47.
First brake adjuster is used to control aircraft air inlet, deflation and the size for adjusting brake pressure.The differentiator that brakes is used
When ensureing that aircraft slides race, left and right wheel is individually braked, to control direction of the aircraft in taking off or alightinging run
And operation being capable of aircraft floor turning.In order to complete the test of first brake adjuster and the differentiator that brakes, as above-mentioned test
The decision design of platform, with continued reference to Fig. 1 and Fig. 6, the 4th test loop includes the be connected with the Three branched pipe road
Six pipelines 53, the 1.5L high pressure colds for being connected quintafurcation pipeline with the 6th pipeline 53, being connected with the 6th pipeline 53
Bottle 9 and the 0.75L low pressure air bottle 10 that is connected with the quintafurcation pipeline, air inlet is sequentially provided with the 6th pipeline 53
Switch, first brake pressure regulator 7 and for measure outlet pressure range be 0-10MPa pressure gauge 23；The quintafurcation
Pipeline is connected on the 6th pipeline 53 of the gas outlet of first brake pressure regulator 7, is sequentially provided with the quintafurcation pipeline
Air inlet switch, brake differentiator 8 and range be 0-10MPa pressure gauge 23.
Second brake modulator is equally used for controlling aircraft air inlet, deflation and the size for adjusting brake pressure.And brake and divide
Orchestration is equally when ensureing that aircraft slides race, left and right wheel individually to be braked, to control aircraft taking off or alightinging run
In direction and operation can aircraft floor turn.In order to complete the test of the second brake modulator and brake distributor, as
The decision design of above-mentioned testboard, with continued reference to Fig. 1 and Fig. 7, the 5th test loop includes and the Three branched pipe road
7th pipeline 54 of connection, the 2L for the 7th pipeline 54 being connected the 6th branch line, being connected with the 7th pipeline 54 are high
Air bottle 12 and the 1L low pressure air bottle 13 being connected with the 6th branch line, be sequentially provided with the 7th pipeline 54 into
Air cock, second brake pressure regulator 5 and for measure outlet pressure range be 0-10MPa pressure gauge 23；Described 6th point
Bye-pass is connected on the 7th pipeline 54 of the second brake pressure regulator 5 gas outlet, is set successively on the 6th branch line
There is the pressure gauge 23 that air inlet switch, brake distributor 11 and range are 0-10MPa.
Brake amplifier is used for accelerating to brake and releasing the action of brake, and scales up going out for brake modulator regulation
Mouth pressure.In order to complete the test of brake amplifier, as the decision design of above-mentioned testboard, with continued reference to Fig. 1 and Fig. 8, institute
State the 0.5L that the 6th test loop includes the 8th pipeline 55 of the 3rd branch path connection and is connected with the 8th pipeline 55
Low pressure gas cylinder 15, air inlet switch, brake amplifier 14 are sequentially provided with the 8th pipeline 55 and for measuring outlet pressure
Range is 0-10MPa pressure gauge 23；The gas outlet of the brake amplifier 14 and the described second brake pressure regulator 5 passes through the 7th
Branch line connects, and the 7th branch line is provided with air inlet switch.
Cylinder is expanded against piston rod motion using cold air and acted with control member.Jettron controls the receipts of cylinder
Put.In order to complete the test of cylinder and jettron, as the decision design of above-mentioned testboard, with continued reference to Fig. 1 and Fig. 9, institute
Stating the 7th test loop includes the 9th pipeline 56 that is connected with the Three branched pipe road and is connected with the 9th pipeline 56
Jettron 27 and the cylinder 44 being connected with the jettron 27, the 9th pipeline 56 is provided with air inlet switch, described
The jettron of jettron 27 is received top fitting 38 and is connected with the cylinder receipts top fitting 40 of the cylinder 44, the jettron 27
Jettron put down ozzle 39 and put down ozzle 41 with the cylinder of the cylinder 44 and be connected.
In order to improve the bleed pressure of tested pneumatic accessories, as the decision design of above-mentioned testboard, referring to Fig. 1 and figure
10, the boost-up circuit includes the tenth pipeline 57 being connected with first pipeline 48, and the outlet side of the tenth pipeline 57 is set
Have an outlet ozzle 37, on the tenth pipeline 57 using this be provided with 5MPa pressure reducers 4, air inlet switch, range as 0-10MPa pressure
Pressure gauge 21, the outlet that table 23, jettron 27, booster 29, the range for measuring booster outlet pressure are 0-25MPa
The pressure gauge 21 that switch, the range for measuring output pressure are 0-25MPa；The jettron of the jettron 27 puts down pipe
Mouth is connected by pipeline with the low pressure chamber of the booster 29, the jettron of the jettron 27 receive top fitting by provided with
The pipeline of check valve 28 is connected with the high pressure chest of the booster 29.
In order to complete the low discharge of aircraft fuel oil ventilation pressure charging system pneumatic accessories and big flow test, as above-mentioned test
The decision design of platform, referring to Fig. 1 and Figure 11, the low discharge test loop includes inlet end and is provided with air inlet ozzle 42 and range
The air inlet pipeline of 0-1.6MPa pressure gauge 24, the air inlet pipeline are connected with multiple flowmeters for testing different flow,
The range of each flowmeter differs, the air inlet pipe between pressure gauge 24 and each flowmeter that the range is 0-1.6MPa
Test switch is equipped with road；It is 0-1.6MPa that the big flow test loop, which includes inlet end to be provided with air inlet ozzle 43 and range,
Pressure gauge 24 air inlet pipeline, it is 10-100m that the air inlet pipeline, which is connected with range,3/ h flowmeter 20, the flowmeter
20 and the range be 0-1.6MPa pressure gauge 24 between be provided with test switch.As decision design, with continued reference to Fig. 1 and figure
11, in the low discharge test loop, air inlet pipeline is connected with the flowmeters of four test different flows, is respectively：Range is
Flowmeter 17 that 16-160mL/min flowmeter 16, range is 0.16-1.60L/min, range 0.1-1m3/ h flowmeter
18th, range 1-10m3/ h flowmeter 19.
After above-mentioned testboard is connected with gas cylinder, 10.8-12.7MPa air pressure can be inputted, then transports to the first test list respectively
Member, the second test cell and flow test units.
1st, plain edition pneumatic accessories is tested：
Cold air can obtain 10.8-12.7MPa source of the gas after air inlet ozzle 1, cold air filter 2 and check valve 3, and bleed pressure can
Measured by the pressure gauge 21 that range is 0-25MPa, after 5MPa pressure reducers 4, brake modulator 5,0.3MPa pressure reducers 6, respectively
5MPa, 1MPa, 0.3MPa source of the gas are formed, opens the first branch line, second branched pipe road, the first pipeline 48 and the 3rd branch
The air cock of pipeline, you can the cold air of pressure needed for acquisition, pressure of compressed air are indicated by pressure gauge 22,23,24,25 respectively.For
Convenient use, should generally make 5MPa pressure reducers 4, brake modulator 5, the outlet pressure of 0.3MPa pressure reducers 6 be respectively 5MPa,
1MPa、0.3MPa。
2nd, special type pneumatic accessories is tested：
(1) electromagnetism cold air valve test
Functional reliability is tested：
When air inlet ozzle is non-aerating, switch on power, adjust variable resistor, since 0 ing it is slow be transferred to electromagnet and send " tick
Clatter " sound stops, and voltage should be not more than 22V, consumption electric current is not more than 3.5A, and connecting the 5th voltage should stablize, and each error is few
Remaining 2V.
When air inlet ozzle is inflated, air pressure 0.98MPa is filled with, is switched on power, as voltage ≯ 22V, tested 5 times, electromagnetism is cold
Air valve answers normal work；Air pressure 6.86MPa is filled with, is switched on power, as voltage ≯ 20V, is tested 5 times, electromagnetism cold air valve should be just
Often work.
Rapidity and continuity test：
Air pressure 1.96-2.94MPa is filled with, voltage 24V, rocking bar is no more than the speed of 2 seconds with every circle, when rotation 1 is enclosed
There must be 12 sound, i.e., cannot wherein have 1 time and not work.
Seal tightness test：
During no power, 0.98MPa, 2.94MPa, 4.9MPa and 6.86MPa air pressure are separately added into, each holding 1 minute, everywhere
Do not allow gas leakage.
Switch on power voltage 24V, is separately added into 0.98MPa, 2.94MPa, 4.9MPa and 6.86MPa air pressure, in each pressure
Lower air leakage ≯ 200 milliliters/second.
Comprehensive test：
Outlet ozzle is connected on spring-compressed cylinder, when voltage is 24V, air inlet 0.98MPa, 2.94MPa, 4.9MPa gas
Pressure, be now powered work, no matter its continuity operating rate, should not produce any slow, gas leakage and other failures.
(2) Aircraft Brake Decompression Valve is tested
Performance test：Air inlet switch is opened, to Aircraft Brake Decompression Valve air inlet input 10.8-12.7MPa air pressure, moves behaviour
Vertical handle, outlet pressure pressure relief ranges 0.3-6.9MPa.
Check valve inlet and outlet speed：
Intake velocity, adjustment decompressed pressure are 6.9MPa, depress control crank rapidly, and the pressure of 1.5 liters of gas cylinders is raised to from 0
The time required to during 6.2MPa, it should be not more than 2 seconds.
Exhaust velocity, control crank is lifted when rapid, the pressure of 1.5 liters of gas cylinders from 6.2MPa be put into 0 liter when the time required to,
It should be not more than 2.5 seconds.
Maximum steering force：No more than 55 kilograms.
Total kilometres：No more than 7 millimeters, wherein, idle stroke is not more than 2.5 millimeters.
(3) pressure-releasing electromagnetic valve is tested
Valve break-in is tested：
Outlet ozzle is blocked, 1.176MPa air pressure is added to air inlet ozzle, connects electromagnet 200 times, it is per minute to be no more than
80-100 times, valve is set to carry out break-in.
Sealing is tested：
1L gas cylinders are opened, 1.764MPa air pressure is added to pressure-releasing electromagnetic valve, is then shut off air inlet switch, kept for 1 minute, entered
0.49MPa is not to be exceeded in the pressure drop of atmospheric pressure table.
Close 0.5L gas cylinders and 1L gas cylinders, disconnect electromagnet, respectively to pressure-releasing electromagnetic valve add 0.196MPa and
1.764MPa air pressure, is then shut off air inlet switch, and each to be kept for 1 minute, the pressure drop of boost gauge should not decline.
Inspection is filled, deflation time：
Electromagnet is connected, the pressure of outlet pressure table is no more than as the time required for 1.764MPa drops to 0.049MPa
1.2 the second.
Electromagnet is disconnected, the pressure of outlet pressure table is no more than 1.2 seconds as the time required for 0 rises to 1.127MPa.
Check the accuracy of work：
0.5L gas cylinders and 1L gas cylinders are disconnected, 1.176MPa is separately added into and respectively connects electromagnet 20 with 1.764MPa air pressure
It is secondary, the moment of electromagnet is being connected every time, and air vent should start to deflate.
Check the minimum of solenoid valve：
0.5L gas cylinders and 1L gas cylinders are disconnected, voltage 18V, adds 1.176MPa air pressure, connects electromagnet 5 times, is connect every time
Moment after logical, air vent should start to deflate.
(4) first brake pressure regulator is tested
Experiment condition：Tested at being 15-30 DEG C in temperature.Input pressure is 4.9MPa.
Sealing is tested：
Inlet chamber, the pressure for adjusting boost gauge is 4.9MPa, is then shut off air inlet switch, is kept for 1 minute, air inlet pressure
The pressure indicated on power table, which declines, to be allowed to be not more than 0.049MPa.
Relief chamber, close 1.5L gas cylinders, with control crank adjust outlet pressure table pressure value decibel be 2.45MPa and
0.49MPa, each to be kept for 1 minute, the pressure indicated on outlet pressure table, which declines, to be allowed to be not more than 0.049MPa.
Check valve work constancy：
Decompressed pressure is adjusted to certain value, i.e. 0.98MPa, 1.47MPa, 2.45MPa, fixes the position for limiting screw,
Control crank, which is pressed onto, to be limited on screw, each to carry out 3 times, and record gained pressure value is not more than 0.098MPa.
Check valve work accuracy：
Decompressed pressure is adjusted to 1.764, the fixed position for limiting screw, then loosens control crank, makes decompression successively
Pressure drops to 1.47MPa, 0.98MPa, 0.49MPa, 0.196MPa, after declining every time onto control crank is shifted to original tune again
Whole position, decompressed pressure recovery value and the pressure difference value of former adjustment should be not more than 0.098MPa.
Check valve inlet and outlet speed：
Intake velocity, it is not less than 9.8MPa in storage pressure, first brake pressure regulator inlet pressure is 4.9MPa situation
Under, decompressed pressure is adjusted to 2.45MPa, depresses control crank rapidly, it is required when decompressed pressure rises to 2.352MPa by 0
Time should be not more than 2 seconds.
Exhaust velocity, it is 2.45MPa to adjust and reduce pressure pressure, and when lifting control crank rapidly, decompressed pressure is declined by 2.45MPa
During value 0.196MPa, the required time should be not more than 2.5 seconds.
(5) differentiator that brakes is tested
Allowable angle of inclination inspection：
Rocking arm is won from neutral position to the inclined maximum angle in any one side is not less than 27 degree.
Sealing is tested：
Rocking arm is placed in neutral position, opens air inlet switch, inputs 2.45MPa pressure, the pressure on outlet pressure table
Power closes air inlet switch when reaching 2.45MPa, kept for 1 minute, and the pressure drop on outlet pressure table is not to be exceeded
0.049MPa.
The rocking arm for the differentiator that brakes gradually is verted from centre position to one side, to pressure left or to right outlet pressure table
Untill dropping to zero.This moment, the pressure on the pressure gauge of another side, which declines, should be not more than 0.049MPa；When rocking arm is to opposite one
While vert, by above-mentioned requirements, another chamber of check brakes differentiator.
The accuracy that works experiment：
Brake differentiator rocking arm is placed in centre position, opens air inlet switch, it is differential to braking then to manipulate reducing valve
Device input 2.45MPa cold air must uniformly enter two gas cylinders after the differentiator that brakes.
Intake and exhaust speed inspection：
Adjusting restraint bolt makes the maximum output pressure of reducing valve be 2.45MPa, and storage pressure must not be less than
9.8MPa。
Two-chamber intake and exhaust speed inspection, rocking arm are placed in centre position, quickly control crank are pressed onto on restraint bolt, when
Pressure on outlet pressure table when reaching 2.352MPa the required time must not exceed 2.5 seconds；Quickly control crank is lifted,
Pressure when dropping to 0.196MPa by 2.45MPa the required time must not exceed 2.5 seconds.
Single-chamber intake and exhaust speed inspection, rocking arm make the exhaust of gas cylinder to every side 20-25 degree that verts, and pressure is by 2.45MPa
Time required for dropping to 0.196MPa is no more than 2 seconds；When rocking arm is retracted into centre position, pressure rises to 2.35MPa by above freezing again,
The required time is no more than 2 seconds.
(6) second brake pressure regulator tests
Sealing is tested：
5.88MPa air pressure is added from air inlet ozzle, is kept for 2 minutes, with neutral soap water inspection, does not allow to leak at sealing
Gas.The pressure of outlet pressure table is transferred to 0.098MPa and 1.176MPa respectively, it is each to be kept for 1 minute, gas leakage is not allowed at sealing.
Performance test：
4.9MPa air pressure is added from air inlet ozzle, adjusts handle stop point, the pressure of outlet pressure table is 0.98MPa, pine
Handle is opened, discharges the air pressure of 2L gas cylinders, handle is then moved into rapidly stop point, pressure is by 0 time for being raised to 0.931MPa
No more than 2.2 seconds.
The pressure of delivery gauge is adjusted to rapid release handle after 0.98MPa, the pressure of 2L gas cylinders is dropped by 0.98MPa
Time to 0.049MPa should be no more than 2.2 seconds.
Constant experiment：
Second brake pressure regulator is adjusted to certain value, the fixed position for limiting screw, control crank is pressed onto restriction spiral shell
Nail on 3-4 times, gained pressure must not exceed 0.049MPa with former adjustment pressure difference value.
Valve work accuracy experiment：
Handle stop point is adjusted, the pressure for making outlet pressure table is 0.784MPa, release handle, when pressure drops to
During 0.588MPa, then handle moved back into stop point, the pressure of outlet ozzle should be not less than 0.735MPa.With above method by pressure
It is sequentially adjusted in being checked item by item to 0.49MPa, 0.392MPa, 0.294MPa, 0.196MPa, 0.098MPa, outlet ozzle
Pressure is not less than 0.735MPa.
(7) brake distributor is tested
Allowable angle of inclination inspection：
Rocking arm is won from neutral position to the inclined maximum angle in any one side is not less than 27 degree.
Regulation experiment：
Rocking arm is placed in neutral position, when rocking arm to any one side tilt be not more than 5 degree when, should be air tight, work as rocking arm
Banking when pressure is down to 0, the pressure of another side does not allow to decline, and examines car another side as stated above.
When rocking arm tilts 14 ± 1 degree, exhaust sound should be heard, now pressure should be down to 1.078MPa, according to real work
Experience, rocking arm are transferred to 14-1 degree preferably, and now pressure is 0.98MPa.
When rocking arm tilts 16 ± 1 degree, pressure should be down to 0.098MPa.
Performance test：
Aeration speed inspection, during single gas, the time that 0.049MPa is dropped to from 0.98MPa is no more than 2.2 seconds；Double-exhaust
When, the time that 0.049MPa is dropped to from 0.98MPa is no more than 3 seconds.
Residual air is tested：
Second brake pressure regulator outlet pressure is adjusted to 0.098MPa, brake distributor rocking arm is then quickly moved, checks
The air pressure of left and right intracavitary should be down to 0 by brake distributor.
The second brake pressure regulator pressure 0.49MPa gently is killed, then moves brake distributor rocking arm to left and right successively, now,
Pressure should be down to 0 by one chamber of brake distributor exhaust.
Sealing is tested：
By brake distributor on test fixture, outlet ozzle is blocked, is then separately added into from air inlet ozzle
0.196MPa, 1.176MPa air pressure, each to be kept for 5 minutes, checking dual brake and left and right single brake with neutral soap water, (rocking arm exists
Extreme position) when sealing, do not answer gas leakage.
(8) amplifier that brakes is tested
Maximum output pressure：
Source of the gas is 4.9MPa, and 1.05 ± 0.05MPa air pressure, brake amplification are inputted from the second brake pressure regulator air outlet adapter
Device outlet pressure is 1.6 ± 1MPa.
Inlet and outlet speed：
Intake velocity, brake amplifier outlet connect 0.5L gas cylinders, input cold air, brake amplification to relief piston top rapidly
When device outlet storage pressure rises to 1.766MPa by 0, required time ≯ 0.8 second.
Exhaust velocity, rapid eliminate manipulate chamber air pressure, and brake amplifier outlet storage pressure is dropped to by 1.766MPa
During 0.05MPa, required time ≯ 0.8 second.
(9) boost-up circuit is tested
10.8-12.7MPa air pressure is filled with to booster air inlet pipeline, booster air inlet switch is opened, passes through pressure regulation
The outlet pressure of 5MPa pressure reducers is transferred to 4.9MPa by switch.
Booster air inlet：
Jettron is pulled to Inlet Position, now air inlet pipeline source of the gas is by jettron, check valve, into booster
High pressure chest, admission pressure by range be 0-10MPa pressure gauge indicate.
Charger boost：
Jettron quickly is pulled to pressurization position, and now, 4.9MPa sources of the gas are by jettron, into the low of booster
Chamber is pressed, the pressure of inlet chamber is indicated by the pressure gauge that range is 0-10MPa.High pressure cavity pressure after charger boost is by measuring
The pressure gauge that the range of atmospheric pressure is 0-25MPa indicates.Outlet pressure should be 4 times of admission pressure, and pressure can rise to 20MPa.
The use of charger boost source of the gas：
After test pneumatic accessories is connected with 20MPa outlet ozzles, the high pressure 20MPa for opening pressurization air source goes out air cock, i.e.,
0-20MPa air pressure can be exported to tested pneumatic accessories.Output pressure is indicated by the pressure gauge that range is 0-25MPa.
(10) cylinder and pneumatic switch testing
Cylinder is tested：
Sealing is tested, and with air pressure capable of being increased from " receipts ", " putting " joint respectively, piston and external shell all should seal.
Performance test, cylinder is received into top connection and is connected with the switch receipts top connection of testboard control panel, is then pulled pneumatic
Switch, you can tested cylinder performance.
Jettron is tested：
Performing leak test, " receipts ", " putting " joint do not block, and switch in " neutrality " position, and from " carrying out gas ", joint is with air pressure capable of being increased,
Do not allow gas leakage at " receipts ", " putting " joint and housing.When rocking arm tilt 5 ° when, " receipts ", " putting " joint do not allow gas leakage still.
Performance test, control panel upper cylinder is received into top connection and is connected with jettron receipts top connection, by control panel
Cylinder, which puts down joint, to be put down joint with jettron and is connected, and then back and forth pulls jettron, cylinder from closing to retractable position
Folding and unfolding is flexible, does not allow gas leakage everywhere.
3rd, aircraft fuel oil ventilation pressure charging system pneumatic accessories test
Because aircraft fuel system pneumatic accessories is relatively more, these annexes are required for sealing to test a considerable part
Make air-flow experiment.To adapt to larger flow rate test scope, the application is divided into two big flow, low discharge parts, can expired
The basic demand of the most fuel oil ventilation pressure charging system annex conventionally tests of foot.In order to ensure higher reliability, the application
The suspended body flowmeter for the non-direct-reading of flowmeter that flow test units use.
When carrying out flow rate test, it is only necessary to the air outlet adapter of tested pneumatic accessories is connected with flowmeter inlet suction port,
Then test switch is opened, you can measure the instantaneous delivery of gas.
Above-described embodiment is used for explaining the present invention, rather than limits the invention, in the spirit and right of the present invention
It is required that protection domain in, to any modifications and changes for making of the present invention, both fall within protection scope of the present invention.
Claims (10)
1. a kind of pneumatic accessories of aircraft universal test platform, including test stage body, the outside of the test stage body be provided with console and
Control panel, it is characterised in that be provided with cold gas system and electrical system in the testboard body, the electrical system with it is described cold
Gas system connects, and is powered for the cold gas system；
The cold gas system includes being used for the first test cell, pneumatically attached for testing special type for testing plain edition pneumatic accessories
Second test cell of part and the flow test units for testing aircraft fuel oil ventilation pressure charging system pneumatic accessories；
First test cell includes the first pipeline that one end is provided with air inlet ozzle (1), the other end is provided with outlet ozzle (35)
(48) pressure gauge (21), the 5MPa pressure reducers that range is 0-25MPa, are sequentially provided with along outgassing direction on first pipeline (48)
(4), brake modulator (5), air cock (46) and range are 0-1.6MPa pressure gauge (22)；First pipeline connects on (48)
There are three branch lines, the first branch line is connected to first between the air inlet ozzle (1) and the 5MPa pressure reducers (4)
On pipeline (48), second branched pipe road and Three branched pipe road are all connected to the 5MPa pressure reducers (4) and the brake adjustment
On the first pipeline (48) between device (5)；The outlet side of each branch line is equipped with outlet ozzle (33,34,36), and described the
The pressure of air cock (46) and range for 0-16MPa is sequentially provided with one branch line and second branched pipe road along outgassing direction
Power table (22), is sequentially provided with air cock (46) on the second branched pipe road and pressure that range is 0-10MPa along outgassing direction
Power table (23), 0.3MPa pressure reducers (6), air cock (46) and amount are sequentially provided with along outgassing direction on the Three branched pipe road
Journey is 0-0.4MPa pressure gauge (25)；
Second test cell is included for the first test loop for testing electromagnetism cold air valve (30), decompression of being braked for test
Second test loop of valve (26), the 3rd test loop for testing pressure-releasing electromagnetic valve (47), for test first brake adjust
4th test loop of depressor (7) and brake differentiator (8), brake pressure regulator (5) and brake distributor for test second
(11) it is the 5th test loop, the 6th test loop for testing brake amplifier (14), gentle for tested cylinder (44)
7th test loop of dynamic switch (27) and the boost-up circuit for increasing tested pneumatic accessories bleed pressure；
The flow test units include being used for test scope in 16ml/min-10m3The low discharge of gas flow is tested back in/h
Road and for test scope in 10-100m3The big flow test loop of gas flow in/h.
2. pneumatic accessories of aircraft universal test platform as claimed in claim 1, it is characterised in that first test loop includes
The second pipeline (49) for being connected with the first pipeline (48), the 3rd pipeline (50) being connected with the 3rd branch path and with the electromagnetism
Cold air valve (30) connection electromagnetism air cock air inlet ozzle (45), second pipeline (49) and the 3rd pipeline (50) are and electromagnetism
Air cock air inlet ozzle (45) connects；Second pipeline (49) connection gas cylinder (31), on second pipeline (49)
It is sequentially provided with the pressure gauge (22) of air inlet switch and range for 0-16MPa；3rd pipeline (50) the connection low pressure gas cylinder (32),
Air inlet switch is sequentially provided with 3rd pipeline (50) provided with the pressure gauge (23) that range is 0-10MPa.
3. pneumatic accessories of aircraft universal test platform as claimed in claim 1, it is characterised in that second test loop includes
The 4th pipeline (51) that is connected with the pipeline of the first pipeline first (48) and to be connected 1.5L with the 4th pipeline (51) high
Air bottle (9) is pressed, it is 0-16MPa to be sequentially provided with air inlet switch, Aircraft Brake Decompression Valve (26) and range on the 4th pipeline (51)
Pressure gauge (22).
4. pneumatic accessories of aircraft universal test platform as claimed in claim 1, it is characterised in that the 3rd test loop includes
The 5th pipeline (52) that is connected with first pipeline (48), the 4th branch line being connected with the 5th pipeline (52), with
The 0.5L low pressure gas cylinders (15) of 5th pipeline (52) connection and the 1L low pressure gas cylinders (13) being connected with the 4th branch line；
5MPa pressure reducers (4) are sequentially provided with 5th pipeline (52), the pressure that the range for measuring admission pressure is 0-10MPa
Table (23), air inlet switch, pressure-releasing electromagnetic valve (47) and for measure outlet pressure range be 0-10MPa pressure gauge
(23)；4th branch line is connected on the 5th pipeline (52) between air inlet switch and the pressure-releasing electromagnetic valve (47).
5. pneumatic accessories of aircraft universal test platform as claimed in claim 1, it is characterised in that the 4th test loop includes
The 6th pipeline (53) that is connected with the Three branched pipe road, with the 6th pipeline (53) it is connected quintafurcation pipeline and institute
State the 1.5L high pressure colds bottle (9) of the 6th pipeline (53) connection and the 0.75L low pressure colds being connected with the quintafurcation pipeline
Gas cylinder (10), air inlet switch, first brake pressure regulator (7) are sequentially provided with and for measuring air pressure on the 6th pipeline (53)
The range of power is 0-10MPa pressure gauge (23)；The quintafurcation pipeline is connected to first brake pressure regulator (7) outlet
On 6th pipeline (53) of mouth, it is 0- that air inlet switch, brake differentiator (8) and range are sequentially provided with the quintafurcation pipeline
10MPa pressure gauge (23).
6. pneumatic accessories of aircraft universal test platform as claimed in claim 1, it is characterised in that the 5th test loop includes
The 7th pipeline (54) that is connected with the Three branched pipe road, with the 7th pipeline (54) it is connected the 6th branch line and institute
The 1L low pressure air bottles stated the 2L gas cylinders (12) of the 7th pipeline (54) connection and be connected with the 6th branch line
(13) air inlet switch, the second brake pressure regulator (5), are sequentially provided with the 7th pipeline (54) and for measuring outlet pressure
Range is 0-10MPa pressure gauge (23)；6th branch line is connected to described second brake pressure regulator (5) gas outlet
On 7th pipeline (54), it is 0- that air inlet switch, brake distributor (11) and range are sequentially provided with the 6th branch line
10MPa pressure gauge (23).
7. pneumatic accessories of aircraft universal test platform as claimed in claim 6, it is characterised in that the 6th test loop includes
8th pipeline (55) of the 3rd branch path connection and the 0.5L low pressure gas cylinders (15) being connected with the 8th pipeline (55), institute
It is 0- to state and air inlet switch, brake amplifier (14) and the range for measuring outlet pressure are sequentially provided with the 8th pipeline (55)
10MPa pressure gauge (23)；The brake amplifier (14) and the gas outlet of the described second brake pressure regulator (5) pass through the 7th point
Bye-pass connects, and the 7th branch line is provided with air inlet switch.
8. pneumatic accessories of aircraft universal test platform as claimed in claim 1, it is characterised in that the 7th test loop includes
The 9th pipeline (56) that is connected with the Three branched pipe road and with jettron (27) that the 9th pipeline (56) is connected with
And the cylinder (44) being connected with the jettron (27), the 9th pipeline (56) is provided with air inlet switch, described pneumatically to open
Close the jettron receipts top fitting (38) of (27) to be connected with the cylinder receipts top fitting (40) of the cylinder (44), the jettron
(27) jettron, which puts down ozzle (39), to be put down ozzle (41) with the cylinder of the cylinder (44) and is connected.
9. pneumatic accessories of aircraft universal test platform as claimed in claim 1, it is characterised in that the boost-up circuit includes and institute
The tenth pipeline (57) of the first pipeline (48) connection is stated, the outlet side of the tenth pipeline (57) is provided with outlet ozzle (37), institute
State on the tenth pipeline (57) using this be provided with 5MPa pressure reducers (4), air inlet switch, range be 0-10MPa pressure gauge (23), pneumatically
Pressure gauge (21), the outlet that switch (27), booster (29), the range for measuring booster outlet pressure are 0-25MPa are opened
Close, the pressure gauge (21) that the range for measuring output pressure is 0-25MPa；The jettron of the jettron (27) is put down
Ozzle is connected by pipeline with the low pressure chamber of the booster (29), and the jettron of the jettron (27) is received top fitting and led to
The pipeline provided with check valve (28) is crossed to be connected with the high pressure chest of the booster (29).
10. pneumatic accessories of aircraft universal test platform as claimed in claim 1, it is characterised in that the low discharge test loop
The air inlet pipeline of air inlet ozzle (42) and range for 0-1.6MPa pressure gauge (24), the air inlet pipeline are provided with including inlet end
Multiple flowmeters for testing different flow are connected with, the range of each flowmeter differs, and the range is 0-
Test switch is equipped with air inlet pipeline between 1.6MPa pressure gauge (24) and each flowmeter；The big flow is tested back
Road includes the air inlet pipeline for the pressure gauge (24) that inlet end is provided with air inlet ozzle (43) and range is 0-1.6MPa, the air inlet pipe
It is 10-100m that road, which is connected with range,3/ h flowmeter (20), the flowmeter (20) and the pressure that the range is 0-1.6MPa
Test switch is provided between table (24).
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109099963A (en) * | 2018-07-04 | 2018-12-28 | 中国航天员科研训练中心 | A kind of multrirange multi output pneumatic control detection device |
| CN109625321A (en) * | 2018-12-29 | 2019-04-16 | 南京王行航空附件维修工程有限公司 | Water power integrated test system |
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| CN202133551U (en) * | 2011-06-29 | 2012-02-01 | 南京王行航空附件维修工程有限公司 | Airplane fuel accessory performance test system |
| CN102589860A (en) * | 2012-01-09 | 2012-07-18 | 中国人民解放军海军航空工程学院青岛分院 | Integrated testing system for aviation fuel accessories |
| CN104655442A (en) * | 2015-02-13 | 2015-05-27 | 中国人民解放军海军航空工程学院青岛校区 | Integrated oil seal system for airplane fuel accessories |
| CN205533548U (en) * | 2016-03-31 | 2016-08-31 | 南京王行航空附件维修工程有限公司 | Aircraft operating system servo control test system |
| CN106249731A (en) * | 2016-06-29 | 2016-12-21 | 赵红军 | A kind of military cockpit pressure regulating system outfield detection device |
| CN207191480U (en) * | 2017-08-01 | 2018-04-06 | 中国人民解放军海军航空工程学院青岛校区 | Pneumatic accessories of aircraft universal test platform |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109099963A (en) * | 2018-07-04 | 2018-12-28 | 中国航天员科研训练中心 | A kind of multrirange multi output pneumatic control detection device |
| CN109625321A (en) * | 2018-12-29 | 2019-04-16 | 南京王行航空附件维修工程有限公司 | Water power integrated test system |
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